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RU2012158395A - TRANSITION NOZZLE AND TURBINE ASSEMBLY - Google Patents

TRANSITION NOZZLE AND TURBINE ASSEMBLY Download PDF

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Publication number
RU2012158395A
RU2012158395A RU2012158395/06A RU2012158395A RU2012158395A RU 2012158395 A RU2012158395 A RU 2012158395A RU 2012158395/06 A RU2012158395/06 A RU 2012158395/06A RU 2012158395 A RU2012158395 A RU 2012158395A RU 2012158395 A RU2012158395 A RU 2012158395A
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RU
Russia
Prior art keywords
cooling
shell
combustion chamber
nozzle
cooling fluid
Prior art date
Application number
RU2012158395/06A
Other languages
Russian (ru)
Inventor
Кевин Уэстон МАКМЭХЭН
Рональд Джеймс ЧАЙЛА
Дэвид Ричард ДЖОНС
Original Assignee
Дженерал Электрик Компани
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Дженерал Электрик Компани filed Critical Дженерал Электрик Компани
Publication of RU2012158395A publication Critical patent/RU2012158395A/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • F05D2260/2322—Heat transfer, e.g. cooling characterized by the cooling medium steam
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03341—Sequential combustion chambers or burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/005—Combined with pressure or heat exchangers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Nozzles (AREA)

Abstract

1. Переходная форсунка (200), предназначенная для использования в узле (100) турбины и содержащаяжаровую трубу (202), ограничивающую внутри себя топочную камеру (208),оболочку (214), окружающую жаровую трубу с образованием между оболочкой и жаровой трубой охлаждающего канала (216),впускное отверстие (230) для охлаждающей текучей среды, предназначенное для подачи охлаждающей текучей среды в охлаждающий канал, иребра (220), присоединенные между жаровой трубой и оболочкой с образованием в охлаждающем канале охлаждающих проходов (222).2. Переходная форсунка (200) по п.1, в которой каждое ребро (220) проходит по существу в окружном направлении вокруг топочной камеры (208) таким образом, что охлаждающие проходы (222) разнесены в осевом направлении.3. Переходная форсунка (200) по п.2, в которой разнесенные в осевом направлении охлаждающие проходы (222) расположены в спиральной конфигурации вокруг топочной камеры (208).4. Переходная форсунка (200) по п.1, в которой каждое ребро (220) проходит в осевом направлении вдоль топочной камеры (208) таким образом, что охлаждающие проходы (222) разнесены в окружном направлении.5. Переходная форсунка (200) по п.1, в которой указанное впускное отверстие (230) для охлаждающей текучей среды образовано в указанной оболочке (214).6. Переходная форсунка (200) по п.1, дополнительно содержащая выпускное отверстие (248) для охлаждающей текучей среды, образованное в указанной оболочке (214) и предназначенное для направления потока охлаждающей текучей среды из охлаждающего канала (216).7. Переходная форсунка (200) по п.1, дополнительно содержащая охлаждающее отверстие (350), образованное в жаровой трубе (202) и обеспечивающее проточное сообщение между охлажда�1. A transitional nozzle (200) intended for use in a turbine assembly (100) and comprising a heat pipe (202) defining a combustion chamber (208) inside, a shell (214) surrounding the heat pipe with the formation of a cooling channel between the shell and the heat pipe (216), a cooling fluid inlet (230) for supplying a cooling fluid to the cooling channel, fins (220) connected between the flame tube and the shell to form cooling passages in the cooling channel (222) .2. A transition nozzle (200) according to claim 1, wherein each rib (220) extends substantially in a circumferential direction around the combustion chamber (208) so that the cooling passages (222) are axially spaced. A transition nozzle (200) according to claim 2, in which axially spaced cooling passages (222) are arranged in a spiral configuration around the combustion chamber (208). 4. A transition nozzle (200) according to claim 1, wherein each rib (220) extends axially along the combustion chamber (208) in such a way that the cooling passages (222) are spaced apart in a circumferential direction. A transition nozzle (200) according to claim 1, wherein said inlet (230) for a cooling fluid is formed in said shell (214) .6. The transition nozzle (200) according to claim 1, further comprising an outlet (248) for the cooling fluid formed in said shell (214) and intended to direct the flow of the cooling fluid from the cooling channel (216). 7. The transition nozzle (200) according to claim 1, further comprising a cooling hole (350) formed in the flame tube (202) and providing flow communication between the cooling�

Claims (10)

1. Переходная форсунка (200), предназначенная для использования в узле (100) турбины и содержащая1. The transitional nozzle (200), intended for use in the node (100) of the turbine and containing жаровую трубу (202), ограничивающую внутри себя топочную камеру (208),a fire tube (202) bounding the combustion chamber (208), оболочку (214), окружающую жаровую трубу с образованием между оболочкой и жаровой трубой охлаждающего канала (216),a shell (214) surrounding the flame tube with the formation of a cooling channel (216) between the shell and the flame tube, впускное отверстие (230) для охлаждающей текучей среды, предназначенное для подачи охлаждающей текучей среды в охлаждающий канал, иa cooling fluid inlet (230) for supplying a cooling fluid to the cooling channel, and ребра (220), присоединенные между жаровой трубой и оболочкой с образованием в охлаждающем канале охлаждающих проходов (222).fins (220) connected between the flame tube and the shell to form cooling passages (222) in the cooling channel. 2. Переходная форсунка (200) по п.1, в которой каждое ребро (220) проходит по существу в окружном направлении вокруг топочной камеры (208) таким образом, что охлаждающие проходы (222) разнесены в осевом направлении.2. The transition nozzle (200) according to claim 1, in which each rib (220) extends essentially in a circumferential direction around the combustion chamber (208) so that the cooling passages (222) are axially spaced. 3. Переходная форсунка (200) по п.2, в которой разнесенные в осевом направлении охлаждающие проходы (222) расположены в спиральной конфигурации вокруг топочной камеры (208).3. The transition nozzle (200) according to claim 2, in which axially spaced cooling passages (222) are arranged in a spiral configuration around the combustion chamber (208). 4. Переходная форсунка (200) по п.1, в которой каждое ребро (220) проходит в осевом направлении вдоль топочной камеры (208) таким образом, что охлаждающие проходы (222) разнесены в окружном направлении.4. The transition nozzle (200) according to claim 1, in which each rib (220) extends axially along the combustion chamber (208) so that the cooling passages (222) are spaced in the circumferential direction. 5. Переходная форсунка (200) по п.1, в которой указанное впускное отверстие (230) для охлаждающей текучей среды образовано в указанной оболочке (214).5. The transition nozzle (200) according to claim 1, wherein said inlet (230) for a cooling fluid is formed in said shell (214). 6. Переходная форсунка (200) по п.1, дополнительно содержащая выпускное отверстие (248) для охлаждающей текучей среды, образованное в указанной оболочке (214) и предназначенное для направления потока охлаждающей текучей среды из охлаждающего канала (216).6. The transition nozzle (200) according to claim 1, further comprising an outlet (248) for the cooling fluid formed in said shell (214) and intended to direct the flow of the cooling fluid from the cooling channel (216). 7. Переходная форсунка (200) по п.1, дополнительно содержащая охлаждающее отверстие (350), образованное в жаровой трубе (202) и обеспечивающее проточное сообщение между охлаждающим каналом (216) и топочной камерой (208).7. The transition nozzle (200) according to claim 1, further comprising a cooling hole (350) formed in the flame tube (202) and providing flow communication between the cooling channel (216) and the combustion chamber (208). 8. Переходная форсунка (200) по п.1, в которой впускное отверстие (230) для охлаждающей текучей среды предназначено для подачи пара в качестве охлаждающей текучей среды.8. The transition nozzle (200) according to claim 1, in which the inlet (230) for the cooling fluid is designed to supply steam as a cooling fluid. 9. Узел (100) турбины, содержащий9. An assembly (100) of a turbine comprising топливную форсунку (210), выполненную с возможностью смешивания топлива и воздуха с созданием топливовоздушной смеси, иa fuel injector (210) configured to mix fuel and air to create a fuel / air mixture, and переходную форсунку (200), ориентированную с обеспечением приема топливовоздушной смеси из указанной топливной форсунки и содержащуюtransitional nozzle (200), oriented to ensure reception of the air-fuel mixture from the specified fuel nozzle and containing жаровую трубу (202), ограничивающую внутри себя топочную камеру (208),a fire tube (202) bounding the combustion chamber (208), оболочку (214), окружающую указанную жаровую трубу с образованием между указанной оболочкой и указанной жаровой трубой охлаждающего канала (216),a shell (214) surrounding said flame tube to form a cooling channel (216) between said shell and said flame tube, впускное отверстие (230) для охлаждающей текучей среды, предназначенное для подачи охлаждающей текучей среды в охлаждающий канал, иa cooling fluid inlet (230) for supplying a cooling fluid to the cooling channel, and ребра (220), расположенные между указанной жаровой трубой и указанной оболочкой с образованием в охлаждающем канале охлаждающих проходов (222).fins (220) located between the specified flame tube and the specified shell with the formation in the cooling channel of the cooling passages (222). 10. Узел (100) турбины по п.9, в котором каждое ребро (220) проходит в окружном направлении вокруг топочной камеры (208) так, что охлаждающие проходы (222) разнесены в осевом направлении. 10. The turbine assembly (100) according to claim 9, wherein each rib (220) extends in a circumferential direction around the combustion chamber (208) so that the cooling passages (222) are axially spaced.
RU2012158395/06A 2012-01-03 2012-12-28 TRANSITION NOZZLE AND TURBINE ASSEMBLY RU2012158395A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/342,475 2012-01-03
US13/342,475 US9243506B2 (en) 2012-01-03 2012-01-03 Methods and systems for cooling a transition nozzle

Publications (1)

Publication Number Publication Date
RU2012158395A true RU2012158395A (en) 2014-07-10

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Family Applications (1)

Application Number Title Priority Date Filing Date
RU2012158395/06A RU2012158395A (en) 2012-01-03 2012-12-28 TRANSITION NOZZLE AND TURBINE ASSEMBLY

Country Status (5)

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US (1) US9243506B2 (en)
EP (1) EP2613002B1 (en)
JP (1) JP6669424B2 (en)
CN (1) CN103185354B (en)
RU (1) RU2012158395A (en)

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9366438B2 (en) * 2013-02-14 2016-06-14 Siemens Aktiengesellschaft Flow sleeve inlet assembly in a gas turbine engine
US9279369B2 (en) * 2013-03-13 2016-03-08 General Electric Company Turbomachine with transition piece having dilution holes and fuel injection system coupled to transition piece
US9080447B2 (en) * 2013-03-21 2015-07-14 General Electric Company Transition duct with divided upstream and downstream portions
US10663169B2 (en) * 2014-07-25 2020-05-26 Mitsubishi Hitachi Power Systems, Ltd. Cylinder for combustor, combustor, and gas turbine
US9915428B2 (en) * 2014-08-20 2018-03-13 Mitsubishi Hitachi Power Systems, Ltd. Cylinder of combustor, method of manufacturing of cylinder of combustor, and pressure vessel
JP6437099B2 (en) * 2014-08-26 2018-12-12 シーメンス エナジー インコーポレイテッド Cooling system for fuel nozzles in a turbine engine combustor.
CN104359124A (en) * 2014-09-19 2015-02-18 北京华清燃气轮机与煤气化联合循环工程技术有限公司 Flow guide bush of combustion chamber of gas turbine
WO2017077955A1 (en) * 2015-11-05 2017-05-11 三菱日立パワーシステムズ株式会社 Combustion cylinder, gas turbine combustor, and gas turbine
KR101863779B1 (en) 2017-09-15 2018-06-01 두산중공업 주식회사 Helicoidal structure for enhancing cooling performance of liner and a gas turbine combustor using the same
US11215072B2 (en) * 2017-10-13 2022-01-04 General Electric Company Aft frame assembly for gas turbine transition piece
US11060484B2 (en) * 2018-06-29 2021-07-13 The Boeing Company Nozzle wall for an air-breathing engine of a vehicle and method therefor
US11248789B2 (en) 2018-12-07 2022-02-15 Raytheon Technologies Corporation Gas turbine engine with integral combustion liner and turbine nozzle
KR102156416B1 (en) * 2019-03-12 2020-09-16 두산중공업 주식회사 Transition piece assembly and transition piece module and combustor and gas turbine comprising the transition piece assembly
US11614233B2 (en) 2020-08-31 2023-03-28 General Electric Company Impingement panel support structure and method of manufacture
US11994293B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus support structure and method of manufacture
US11460191B2 (en) 2020-08-31 2022-10-04 General Electric Company Cooling insert for a turbomachine
US11371702B2 (en) 2020-08-31 2022-06-28 General Electric Company Impingement panel for a turbomachine
US11994292B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus for turbomachine
US11255545B1 (en) 2020-10-26 2022-02-22 General Electric Company Integrated combustion nozzle having a unified head end
US11767766B1 (en) 2022-07-29 2023-09-26 General Electric Company Turbomachine airfoil having impingement cooling passages

Family Cites Families (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2910828A (en) * 1956-08-24 1959-11-03 United Aircraft Company Convergent-divergent variable area propulsion nozzle
US3344606A (en) * 1961-09-27 1967-10-03 United Aircraft Corp Recover bleed air turbojet
US3584972A (en) * 1966-02-09 1971-06-15 Gen Motors Corp Laminated porous metal
US4195474A (en) * 1977-10-17 1980-04-01 General Electric Company Liquid-cooled transition member to turbine inlet
US4314442A (en) * 1978-10-26 1982-02-09 Rice Ivan G Steam-cooled blading with steam thermal barrier for reheat gas turbine combined with steam turbine
US4438625A (en) * 1978-10-26 1984-03-27 Rice Ivan G Reheat gas turbine combined with steam turbine
FR2495736A1 (en) * 1980-12-05 1982-06-11 Air Liquide METHOD AND PLANT FOR TREATING ENERGY RECOVERED WASTE
US4543781A (en) * 1981-06-17 1985-10-01 Rice Ivan G Annular combustor for gas turbine
US4928478A (en) * 1985-07-22 1990-05-29 General Electric Company Water and steam injection in cogeneration system
JPH09196377A (en) * 1996-01-12 1997-07-29 Hitachi Ltd Gas turbine combustor
US5724816A (en) * 1996-04-10 1998-03-10 General Electric Company Combustor for a gas turbine with cooling structure
JP3069522B2 (en) * 1996-05-31 2000-07-24 株式会社東芝 Gas turbine combustor
US5933699A (en) * 1996-06-24 1999-08-03 General Electric Company Method of making double-walled turbine components from pre-consolidated assemblies
JPH1082527A (en) * 1996-09-05 1998-03-31 Toshiba Corp Gas turbine combustor
DE19751299C2 (en) * 1997-11-19 1999-09-09 Siemens Ag Combustion chamber and method for steam cooling a combustion chamber
JP2000088252A (en) * 1998-09-11 2000-03-31 Hitachi Ltd Gas turbine with cooling promotion structure
JP4274666B2 (en) 2000-03-07 2009-06-10 三菱重工業株式会社 gas turbine
JP2001271655A (en) * 2000-03-24 2001-10-05 Mitsubishi Heavy Ind Ltd Circulating air-cooled gas turbine
JP2001289062A (en) * 2000-04-07 2001-10-19 Mitsubishi Heavy Ind Ltd Wall surface cooling structure for gas turbine combustor
US20050044857A1 (en) * 2003-08-26 2005-03-03 Boris Glezer Combustor of a gas turbine engine
US6890148B2 (en) 2003-08-28 2005-05-10 Siemens Westinghouse Power Corporation Transition duct cooling system
US7310938B2 (en) * 2004-12-16 2007-12-25 Siemens Power Generation, Inc. Cooled gas turbine transition duct
US7401682B2 (en) * 2005-08-10 2008-07-22 United Technologies Corporation Architecture for an acoustic liner
US7827801B2 (en) * 2006-02-09 2010-11-09 Siemens Energy, Inc. Gas turbine engine transitions comprising closed cooled transition cooling channels
US7757492B2 (en) * 2007-05-18 2010-07-20 General Electric Company Method and apparatus to facilitate cooling turbine engines
US8096752B2 (en) * 2009-01-06 2012-01-17 General Electric Company Method and apparatus for cooling a transition piece
US8549861B2 (en) * 2009-01-07 2013-10-08 General Electric Company Method and apparatus to enhance transition duct cooling in a gas turbine engine
US8307657B2 (en) 2009-03-10 2012-11-13 General Electric Company Combustor liner cooling system
US8015817B2 (en) * 2009-06-10 2011-09-13 Siemens Energy, Inc. Cooling structure for gas turbine transition duct
US20110239654A1 (en) * 2010-04-06 2011-10-06 Gas Turbine Efficiency Sweden Ab Angled seal cooling system
US9133721B2 (en) * 2010-11-15 2015-09-15 Siemens Energy, Inc. Turbine transition component formed from a two section, air-cooled multi-layer outer panel for use in a gas turbine engine
US9097117B2 (en) * 2010-11-15 2015-08-04 Siemens Energy, Inc Turbine transition component formed from an air-cooled multi-layer outer panel for use in a gas turbine engine
JP2012145098A (en) * 2010-12-21 2012-08-02 Toshiba Corp Transition piece, and gas turbine
US8727714B2 (en) * 2011-04-27 2014-05-20 Siemens Energy, Inc. Method of forming a multi-panel outer wall of a component for use in a gas turbine engine

Also Published As

Publication number Publication date
EP2613002B1 (en) 2024-02-14
US9243506B2 (en) 2016-01-26
CN103185354B (en) 2016-12-28
US20130167543A1 (en) 2013-07-04
JP6669424B2 (en) 2020-03-18
CN103185354A (en) 2013-07-03
EP2613002A2 (en) 2013-07-10
EP2613002A3 (en) 2017-08-09
JP2013139799A (en) 2013-07-18

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